CA2507086A1 - Turbine blade nested seal damper assembly - Google Patents
Turbine blade nested seal damper assembly Download PDFInfo
- Publication number
- CA2507086A1 CA2507086A1 CA002507086A CA2507086A CA2507086A1 CA 2507086 A1 CA2507086 A1 CA 2507086A1 CA 002507086 A CA002507086 A CA 002507086A CA 2507086 A CA2507086 A CA 2507086A CA 2507086 A1 CA2507086 A1 CA 2507086A1
- Authority
- CA
- Canada
- Prior art keywords
- damper
- seal
- recited
- assembly
- turbine blade
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
- F01D11/006—Sealing the gap between rotor blades or blades and rotor
- F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
- F01D11/006—Sealing the gap between rotor blades or blades and rotor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/04—Antivibration arrangements
- F01D25/06—Antivibration arrangements for preventing blade vibration
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/10—Anti- vibration means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/16—Form or construction for counteracting blade vibration
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
Abstract
A turbine blade damper seal assembly includes a seal and a damper that both abut a radially outermost non-gas path surface. The seal is fabricated from a plastically deformable material and nests within a recess of the damper. The damper is fabricated from a rigid material that absorbs vibrational energy generated during operation. The recess within the damper provides for both the damper and the seal to be positioned at the radially outermost non-gas path surface.
Description
TURBINE BLADE NESTED SEAL DAMPER ASSEMBLY
BACKGROUND OF THE INVENTION
This application relates generally to a turbine seal and damper assembly and specifically to a nested seal and damper assembly.
Conventional gas turbine engines include a turbine assembly that has a plurality of turbine blades attached about a circumference of a turbine rotor.
Each of the turbine blades is spaced a distance apart from adjacent turbine blades to accommodate movement and expansion during operation. The blades typically include a root that attaches to the rotor, a platform and a blade that extends radially outwardly from the platform.
Problems arise when hot gases penetrate below the platform of the turbine blades. Hot gases flowing over the platform are prevented from leaking between adjacent turbine blades by a seal. This is done because components below the platform are generally not designed to operate for extended durations at the elevated temperatures of the hot gases. The seal is typically a metal sheet nested between adjacent turbine blades on an inner surface of the platform. The seal is typically flexible so as to conform to the inner surface of the platform and prevent the intrusion of hot gases below the platform of the turbine blade. Typically, the seal is disposed against a radially outboard inner surface of the platform of the turbine blade.
In addition to the seal it is common practice to include a damper between adjacent turbine blades to dissipate potentially damaging vibrations. A damper is typically sized to provide sufficient mass and rigidity to dissipate vibration from the turbine blade. Vibrations from the turbine blade are transmitted through frictional contact between the damper and an inner surface of the turbine blade platform.
Dampers provide the maximum benefit and dampening when positioned at a radial outermost part of an inner surface of the platform.
Disadvantageously, both the damper and the seal perform to the maximum benefit when positioned against the inner surface of the platform. As appreciated, it is only possible to position either the seal or the damper immediately adjacent the inner surface.
A currently proposed solution provides a single part that performs as both the seal and as the damper. Such a device provides for the desired location of both the damper and the seal. However, the material properties of the seal and the damper are compromised to accommodate the separate functions. That is the seal material is not as flexible as desired in order to provide the dampening properties required and the damper material does not provide the most beneficial dampening properties in order to provide some flexibility for the seal. The compromise between favorable dampening properties and favorable seal properties yields less than desirable performance for both functions.
Accordingly, it is desirable to develop a seal and damper assembly utilizing the most beneficial material for each function while providing the most beneficial placement of the damper and seal.
SUMMARY OF THE INVENTION
This invention is a damper-seal assembly for a turbine blade that includes a seal nested within a damper such that both the seal and damper are disposed at an interior outer most surface of the turbine blade.
The damper-seal assembly includes the seal that prevents hot gases from penetrating a gap between adjacent turbine blades. The seal abuts the inner surface of the platform and bridges the gap to block the flow of hot gases. The damper includes a recess within which the seal nests. On each side of the recess the damper includes a surface that contacts the inner most surfaces of the turbine blade.
The surface of the damper provides frictional contact that absorbs vibrational energy from the turbine blade generated during operation.
The damper-seal assembly is assembled within a cavity of the turbine blade such that both the damper and the seal are adjacent the inner surface. Both the damper and the seal provide the most benefit by being located at the radially outermost point within the cavity.
BACKGROUND OF THE INVENTION
This application relates generally to a turbine seal and damper assembly and specifically to a nested seal and damper assembly.
Conventional gas turbine engines include a turbine assembly that has a plurality of turbine blades attached about a circumference of a turbine rotor.
Each of the turbine blades is spaced a distance apart from adjacent turbine blades to accommodate movement and expansion during operation. The blades typically include a root that attaches to the rotor, a platform and a blade that extends radially outwardly from the platform.
Problems arise when hot gases penetrate below the platform of the turbine blades. Hot gases flowing over the platform are prevented from leaking between adjacent turbine blades by a seal. This is done because components below the platform are generally not designed to operate for extended durations at the elevated temperatures of the hot gases. The seal is typically a metal sheet nested between adjacent turbine blades on an inner surface of the platform. The seal is typically flexible so as to conform to the inner surface of the platform and prevent the intrusion of hot gases below the platform of the turbine blade. Typically, the seal is disposed against a radially outboard inner surface of the platform of the turbine blade.
In addition to the seal it is common practice to include a damper between adjacent turbine blades to dissipate potentially damaging vibrations. A damper is typically sized to provide sufficient mass and rigidity to dissipate vibration from the turbine blade. Vibrations from the turbine blade are transmitted through frictional contact between the damper and an inner surface of the turbine blade platform.
Dampers provide the maximum benefit and dampening when positioned at a radial outermost part of an inner surface of the platform.
Disadvantageously, both the damper and the seal perform to the maximum benefit when positioned against the inner surface of the platform. As appreciated, it is only possible to position either the seal or the damper immediately adjacent the inner surface.
A currently proposed solution provides a single part that performs as both the seal and as the damper. Such a device provides for the desired location of both the damper and the seal. However, the material properties of the seal and the damper are compromised to accommodate the separate functions. That is the seal material is not as flexible as desired in order to provide the dampening properties required and the damper material does not provide the most beneficial dampening properties in order to provide some flexibility for the seal. The compromise between favorable dampening properties and favorable seal properties yields less than desirable performance for both functions.
Accordingly, it is desirable to develop a seal and damper assembly utilizing the most beneficial material for each function while providing the most beneficial placement of the damper and seal.
SUMMARY OF THE INVENTION
This invention is a damper-seal assembly for a turbine blade that includes a seal nested within a damper such that both the seal and damper are disposed at an interior outer most surface of the turbine blade.
The damper-seal assembly includes the seal that prevents hot gases from penetrating a gap between adjacent turbine blades. The seal abuts the inner surface of the platform and bridges the gap to block the flow of hot gases. The damper includes a recess within which the seal nests. On each side of the recess the damper includes a surface that contacts the inner most surfaces of the turbine blade.
The surface of the damper provides frictional contact that absorbs vibrational energy from the turbine blade generated during operation.
The damper-seal assembly is assembled within a cavity of the turbine blade such that both the damper and the seal are adjacent the inner surface. Both the damper and the seal provide the most benefit by being located at the radially outermost point within the cavity.
The damper-seal assembly of this invention provides for the use of separate material for the seal and the damper while providing for optimal placement of both the seal and the damper. The seal includes a plastically deformable material that provides the desired seal to prevent the intrusion of hot gases and the damper provides the dense rigid structure necessary for absorbing vibrational energy generated during operation.
Accordingly, the damper-seal assembly of this invention provides for the most beneficial material for each function and the most beneficial placement of the damper and seal.
These and other features of the present invention can be best understood from the following specification and drawings, the following of which is a brief description.
BRIEF DESCRIPTION OF THE DRAWINGS
Figure 1 is a perspective view of adjacent turbine blade assemblies.
Figure 2 is a side view of a damper seal assembly within the turbine blade.
Figure 3 is an exploded view of the damper seal assembly.
Figure 4 is a perspective view of the damper seal assembly.
Figure 5 is a schematic view of placement of the damper seal assembly.
DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT
Referring to Figure 1, a turbine assembly 10 includes a plurality of adjacent turbine blades 12. Each of the turbine bladesl2 includes a root 14 that is fit into a radial slot of a turbine rotor (not shown). Radially outward of the root 14 is a platform 16. The platform 16 includes an outer surface 18 and an inner surface 20.
The inner surface 20 is disposed radially inward of the outer surface 18. An airfoil 22 extends upward from the platform 16.
Hot gas 24 flows around the airfoil 22 and over the outer surface 18. A gap 26 extends axially between adjacent turbine blades 12. The gap 26 prevents contact between the turbine blades 12. A damper-seal assembly 28 includes a seal 30 that prevents hot gases 24 from penetrating the gap 26 and penetrating the underside of the platform 16. The seal 30 is positioned within a cavity 32 formed between adjacent turbine blades 12. The seal 30 abuts the inner surface 20 of the platform 16 and bridges the gap 26 to block the flow of hot gases. The cavity 32 of the turbine blade 12 includes a nub 36 for aligning and positioning the damper-seal assembly 28.
Refernng to Figure 2, the damper-seal assembly 28 is assembled within the cavity 32 of the turbine blade 12 such that both the damper 34 and the seal 30 are adjacent the inner surface 20. Both the damper 34 and the seal 30 provide the most benefit by being located at the radially outermost point within the cavity 32.
The radial most position is where the damper 34 abuts and is in frictional contact with the inner surface 20. Frictional contact between the damper 34 and the inner surface absorbs and dissipates vibrational energy generated during operation. Axial placement of the damper 34 substantially maximizes vibration-dampening performance. Preferably, the damper 34 is positioned within the cavity 32 to maximize vibration-dampening performance. The damper 34 is illustrated in a 15 forward most position. Although the damper 34 is shown in the forward most position, one skilled in the art with the benefit of this disclosure would understand that other configurations of the damper 34 are within the contemplation of this invention.
Referring to Figures 3 and 4, the seal 30 nests within a recess 38 of the 20 damper 34. The recess 38 provides for the seal 30 and a portion of the damper 34 to both abut the inner surface 20 of the platform 16. The recess 38 extends axially along a top surface of the damper 34. The seal 30 includes fingers 44 that interfit onto the damper 34 and secure the seal 30 and the damper 34 together. The fit between the damper 34 positions the seal 30 relative to the damper 34 and thereby relative to the gap 26 between adjacent turbine blades 12.
The damper 34 includes a body portion 50 and seal retention arms 52 that extend forward of the body portion 50 for supporting a forward portion of the seal 30. The damper 34 includes rub surfaces 46 disposed on either side of the recess 38.
The rub surfaces 46 are in frictional contact with the inner surface 20 along a plane common with the seal 30. The damper 34 includes retention features 54 that correspond to the cavity 32 to position and secure the damper-seal assembly 28 relative to the inner surface 20. An alignment feature 56 is also included and juts from the body 50 on each side of the damper 34. Stiffening portions 58 extend the rub surfaces 46 on each side of the damper 34. The stiffening portions 58 strengthen and reinforce the rub surfaces 46.
The damper 34 is fabricated from a material that does not plastically deform under the thermal and centrifugal loads produced during operation. Further the material utilized for the damper 34 is selected to provide desired vibration dampening properties in addition to the thermal capacity. The damper 34 is placed under centrifugal loading against the inner surface 20 of the platform 16.
Although a preferred configuration of the damper 34 is shown, a worker with the benefit of this disclosure would understand that different configurations and features of the damper 34 are within the contemplation of this invention and dependent on application specific requirements.
The seal 30 is preferably a thin sheet of metal that includes a forward portion 60 that fits onto the retention arms 52 of the damper 34. The fingers 44 interfit the damper 34 and hold the seal 30 nested within the recess 38. The seal 30 is preferably flexible to conform to the inner surface 20 to provide a desired seal against the intrusion of hot gases 24 under the turbine blade 12. A rearward portion 62 extends axially rearward and extends inboard to conform and seal with the configuration of the axially extending gap 26. The material utilized for the seal 30 is selected to withstand the pressures and temperatures associated with a specific application and to allow for some plastic deformation. The seal 30 plastically deforms responsive to the thermal and centrifugal loads to conform and fit the contours of the inner surface 20. The plastic deformation provides a desired seal against the intrusion of hot gases 24.
Refernng to Figure 5, the damper-seal assembly 28 is shown within the cavity 32 defined by adjacent turbine blades 12. The rub surfaces 46 contact the inner surface 20. The damper 34 performs the most benefit at the radially outer most portion on a non-gas path side of the turbine blade 12. The frictional contact between the damper 34 and the inner surface 20 of the turbine blade 12 dampens vibrations generated during operation. The seal 30 is disposed along the axial gap 26 on the inner surface 20. The recess 38 provides for continuous contact of the seal 30 along the inner surface 20 of adjacent turbine blades 12 along the entire axial gap 26 while providing the beneficial outermost radial position for the damper 34.
The damper-seal assembly 2$ of this invention provides for the use of separate material for the seal 30 and the damper 34 while providing for optimal placement of both the seal 30 and the damper 34. The seal 30 includes a plastically deformable material that provides the desired seal to prevent the intrusion of hot gases 24 and the damper 34 provides the dense rigid structure necessary for absorbing vibrational energy generated during operation.
Although a preferred embodiment of this invention has been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of this invention. For that reason, the following claims should be studied to determine the true scope and content of this invention.
Accordingly, the damper-seal assembly of this invention provides for the most beneficial material for each function and the most beneficial placement of the damper and seal.
These and other features of the present invention can be best understood from the following specification and drawings, the following of which is a brief description.
BRIEF DESCRIPTION OF THE DRAWINGS
Figure 1 is a perspective view of adjacent turbine blade assemblies.
Figure 2 is a side view of a damper seal assembly within the turbine blade.
Figure 3 is an exploded view of the damper seal assembly.
Figure 4 is a perspective view of the damper seal assembly.
Figure 5 is a schematic view of placement of the damper seal assembly.
DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT
Referring to Figure 1, a turbine assembly 10 includes a plurality of adjacent turbine blades 12. Each of the turbine bladesl2 includes a root 14 that is fit into a radial slot of a turbine rotor (not shown). Radially outward of the root 14 is a platform 16. The platform 16 includes an outer surface 18 and an inner surface 20.
The inner surface 20 is disposed radially inward of the outer surface 18. An airfoil 22 extends upward from the platform 16.
Hot gas 24 flows around the airfoil 22 and over the outer surface 18. A gap 26 extends axially between adjacent turbine blades 12. The gap 26 prevents contact between the turbine blades 12. A damper-seal assembly 28 includes a seal 30 that prevents hot gases 24 from penetrating the gap 26 and penetrating the underside of the platform 16. The seal 30 is positioned within a cavity 32 formed between adjacent turbine blades 12. The seal 30 abuts the inner surface 20 of the platform 16 and bridges the gap 26 to block the flow of hot gases. The cavity 32 of the turbine blade 12 includes a nub 36 for aligning and positioning the damper-seal assembly 28.
Refernng to Figure 2, the damper-seal assembly 28 is assembled within the cavity 32 of the turbine blade 12 such that both the damper 34 and the seal 30 are adjacent the inner surface 20. Both the damper 34 and the seal 30 provide the most benefit by being located at the radially outermost point within the cavity 32.
The radial most position is where the damper 34 abuts and is in frictional contact with the inner surface 20. Frictional contact between the damper 34 and the inner surface absorbs and dissipates vibrational energy generated during operation. Axial placement of the damper 34 substantially maximizes vibration-dampening performance. Preferably, the damper 34 is positioned within the cavity 32 to maximize vibration-dampening performance. The damper 34 is illustrated in a 15 forward most position. Although the damper 34 is shown in the forward most position, one skilled in the art with the benefit of this disclosure would understand that other configurations of the damper 34 are within the contemplation of this invention.
Referring to Figures 3 and 4, the seal 30 nests within a recess 38 of the 20 damper 34. The recess 38 provides for the seal 30 and a portion of the damper 34 to both abut the inner surface 20 of the platform 16. The recess 38 extends axially along a top surface of the damper 34. The seal 30 includes fingers 44 that interfit onto the damper 34 and secure the seal 30 and the damper 34 together. The fit between the damper 34 positions the seal 30 relative to the damper 34 and thereby relative to the gap 26 between adjacent turbine blades 12.
The damper 34 includes a body portion 50 and seal retention arms 52 that extend forward of the body portion 50 for supporting a forward portion of the seal 30. The damper 34 includes rub surfaces 46 disposed on either side of the recess 38.
The rub surfaces 46 are in frictional contact with the inner surface 20 along a plane common with the seal 30. The damper 34 includes retention features 54 that correspond to the cavity 32 to position and secure the damper-seal assembly 28 relative to the inner surface 20. An alignment feature 56 is also included and juts from the body 50 on each side of the damper 34. Stiffening portions 58 extend the rub surfaces 46 on each side of the damper 34. The stiffening portions 58 strengthen and reinforce the rub surfaces 46.
The damper 34 is fabricated from a material that does not plastically deform under the thermal and centrifugal loads produced during operation. Further the material utilized for the damper 34 is selected to provide desired vibration dampening properties in addition to the thermal capacity. The damper 34 is placed under centrifugal loading against the inner surface 20 of the platform 16.
Although a preferred configuration of the damper 34 is shown, a worker with the benefit of this disclosure would understand that different configurations and features of the damper 34 are within the contemplation of this invention and dependent on application specific requirements.
The seal 30 is preferably a thin sheet of metal that includes a forward portion 60 that fits onto the retention arms 52 of the damper 34. The fingers 44 interfit the damper 34 and hold the seal 30 nested within the recess 38. The seal 30 is preferably flexible to conform to the inner surface 20 to provide a desired seal against the intrusion of hot gases 24 under the turbine blade 12. A rearward portion 62 extends axially rearward and extends inboard to conform and seal with the configuration of the axially extending gap 26. The material utilized for the seal 30 is selected to withstand the pressures and temperatures associated with a specific application and to allow for some plastic deformation. The seal 30 plastically deforms responsive to the thermal and centrifugal loads to conform and fit the contours of the inner surface 20. The plastic deformation provides a desired seal against the intrusion of hot gases 24.
Refernng to Figure 5, the damper-seal assembly 28 is shown within the cavity 32 defined by adjacent turbine blades 12. The rub surfaces 46 contact the inner surface 20. The damper 34 performs the most benefit at the radially outer most portion on a non-gas path side of the turbine blade 12. The frictional contact between the damper 34 and the inner surface 20 of the turbine blade 12 dampens vibrations generated during operation. The seal 30 is disposed along the axial gap 26 on the inner surface 20. The recess 38 provides for continuous contact of the seal 30 along the inner surface 20 of adjacent turbine blades 12 along the entire axial gap 26 while providing the beneficial outermost radial position for the damper 34.
The damper-seal assembly 2$ of this invention provides for the use of separate material for the seal 30 and the damper 34 while providing for optimal placement of both the seal 30 and the damper 34. The seal 30 includes a plastically deformable material that provides the desired seal to prevent the intrusion of hot gases 24 and the damper 34 provides the dense rigid structure necessary for absorbing vibrational energy generated during operation.
Although a preferred embodiment of this invention has been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of this invention. For that reason, the following claims should be studied to determine the true scope and content of this invention.
Claims (30)
1. A turbine assembly comprising:
a plurality of turbine blades spaced apart from each other, wherein each of said plurality of turbine blades includes an inner surface radially inboard of an outer surface;
a damper comprising a portion disposed adjacent said inner surface; and a seal nested with said damper and disposed adjacent said inner surface.
a plurality of turbine blades spaced apart from each other, wherein each of said plurality of turbine blades includes an inner surface radially inboard of an outer surface;
a damper comprising a portion disposed adjacent said inner surface; and a seal nested with said damper and disposed adjacent said inner surface.
2. The assembly as recited in claim 1, wherein said damper comprises a recess into which said seal nests.
3. The assembly as recited in claim 1, wherein said seal comprises tab portions that fit onto said damper.
4. The assembly as recited in claim 3, wherein said damper comprises alignment features for aligning said damper relative to each of said plurality of turbine blades.
5. The assembly as recited in claim 4, wherein said alignment features include nubs projecting outwardly.
6. The assembly as recited in claim 1, wherein each of said plurality of turbine blades comprises a forward portion and a rearward portion and said inner and outer surfaces extend therebetween, said damper disposed adjacent said forward portion.
7. The assembly as recited in claim 1, wherein said seal comprises a thin sheet of metal.
8. The assembly as recited in claim 1, wherein said damper comprises a molded mass.
9. The assembly as recited in claim 1, wherein said damper and said seal are both disposed in a radially most outboard position.
10. The assembly as recited in claim 1, wherein adjacent turbine blades define a cavity into which said damper and seal are disposed.
11. The assembly as recited in claim 10 wherein said damper is disposed in a forward most portion of said cavity.
12. The assembly as recited in claim 11, wherein each of said plurality of turbine blades include an alignment feature for positioning said damper within said cavity.
13. A damper seal assembly for a turbine blade comprising:
a damper comprising a contact surface abutting an inner surface of the turbine blade; and a seal nested with said damper abutting the inner surface of the turbine blade.
a damper comprising a contact surface abutting an inner surface of the turbine blade; and a seal nested with said damper abutting the inner surface of the turbine blade.
14. The assembly as recited in claim 13, wherein said damper comprises a recessed portion into which said seal nests.
15. The assembly as recited in claim 13, including a plane defined across said damper by said contact surface wherein a surface of said seal is disposed within said plane.
16. The assembly as recited in claim13, wherein said damper includes retention features corresponding with the inner surface of the turbine blade.
17. The assembly as recited in claim 13, wherein a surface of said seal and said contact surface of said damper abut a radially outermost non-gas path side of the turbine blade.
18. A damper seal assembly comprising:
a damper comprising a body and at least two rub surfaces extending from the body and separated from each other by a recess; and a seal comprising a forward portion with fingers projecting therefrom and a rearward portion projecting at least in part co-directionally with the fingers.
a damper comprising a body and at least two rub surfaces extending from the body and separated from each other by a recess; and a seal comprising a forward portion with fingers projecting therefrom and a rearward portion projecting at least in part co-directionally with the fingers.
19. The assembly as recited in claim 18, wherein said seal includes tab portions that fit onto said damper.
20. The assembly as recited in claim 19, wherein said seal is adapted to fit within said recess of said body.
21. The assembly as recited in claim 20, wherein said at least two rub surfaces and a surface of said seal form a common plane.
22. A damper comprising:
a body; and at least two rub surfaces extending from the body and separate from each other by a recess.
a body; and at least two rub surfaces extending from the body and separate from each other by a recess.
23. The damper as recited in claim 22, including at least one finger extending longitudinally from said body.
24. The damper as recited in claim 22, wherein said at least two rub surfaces extend longitudinally along said body.
25. The damper as recited in claim 22, including at least one lug extending laterally from said body.
26. The damper as recited in claim 22, including at least two lugs disposed on opposite sides of said body.
27. A seal comprising:
a forward segment including fingers projecting therefrom; and a rearward segment projecting at least in part co-directionally with said fingers.
a forward segment including fingers projecting therefrom; and a rearward segment projecting at least in part co-directionally with said fingers.
28. The seal as recited in claim 27, including a body segment defining a plane, wherein said fingers project at least in part transverse to said plane.
29. The seal as recited in claim 28 including at least two fingers projecting transversely from said body segment on a common side.
30. The seal as recited in claim 29, wherein said at least two fingers are spaced a distance apart.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US10/939,766 | 2004-09-13 | ||
| US10/939,766 US7121800B2 (en) | 2004-09-13 | 2004-09-13 | Turbine blade nested seal damper assembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA2507086A1 true CA2507086A1 (en) | 2006-03-13 |
Family
ID=35241055
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA002507086A Abandoned CA2507086A1 (en) | 2004-09-13 | 2005-05-11 | Turbine blade nested seal damper assembly |
Country Status (9)
| Country | Link |
|---|---|
| US (1) | US7121800B2 (en) |
| EP (1) | EP1635037A3 (en) |
| JP (1) | JP2006077759A (en) |
| KR (1) | KR20060048029A (en) |
| CN (1) | CN1749531A (en) |
| AU (1) | AU2005202260B2 (en) |
| CA (1) | CA2507086A1 (en) |
| NO (1) | NO20052830L (en) |
| SG (1) | SG121034A1 (en) |
Families Citing this family (71)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB0611031D0 (en) | 2006-06-06 | 2006-07-12 | Rolls Royce Plc | An aerofoil stage and a seal for use therein |
| GB2446812A (en) * | 2007-02-21 | 2008-08-27 | Rolls Royce Plc | Damping member positioned between blades of an aerofoil assembly |
| US8011892B2 (en) * | 2007-06-28 | 2011-09-06 | United Technologies Corporation | Turbine blade nested seal and damper assembly |
| EP2201271B1 (en) * | 2007-10-25 | 2012-03-14 | Siemens Aktiengesellschaft | Turbine blade assembly and seal strip |
| EP2053286A1 (en) * | 2007-10-25 | 2009-04-29 | Siemens Aktiengesellschaft | Seal strip and turbine blade assembly |
| US7918265B2 (en) * | 2008-02-14 | 2011-04-05 | United Technologies Corporation | Method and apparatus for as-cast seal on turbine blades |
| US8070448B2 (en) * | 2008-10-30 | 2011-12-06 | Honeywell International Inc. | Spacers and turbines |
| US8393869B2 (en) * | 2008-12-19 | 2013-03-12 | Solar Turbines Inc. | Turbine blade assembly including a damper |
| US8167566B2 (en) * | 2008-12-31 | 2012-05-01 | General Electric Company | Rotor dovetail hook-to-hook fit |
| EP2406464B1 (en) | 2009-03-09 | 2015-05-06 | GE Avio S.r.l. | Rotor for turbomachines |
| EP2406465B1 (en) * | 2009-03-09 | 2015-05-06 | GE Avio S.r.l. | Rotor for turbomachines with shrouded blades |
| US20100232939A1 (en) * | 2009-03-12 | 2010-09-16 | General Electric Company | Machine Seal Assembly |
| US8696320B2 (en) * | 2009-03-12 | 2014-04-15 | General Electric Company | Gas turbine having seal assembly with coverplate and seal |
| US8529201B2 (en) * | 2009-12-17 | 2013-09-10 | United Technologies Corporation | Blade outer air seal formed of stacked panels |
| US8672626B2 (en) | 2010-04-21 | 2014-03-18 | United Technologies Corporation | Engine assembled seal |
| FR2963383B1 (en) * | 2010-07-27 | 2016-09-09 | Snecma | DUST OF TURBOMACHINE, ROTOR, LOW PRESSURE TURBINE AND TURBOMACHINE EQUIPPED WITH SUCH A DAWN |
| US8790086B2 (en) | 2010-11-11 | 2014-07-29 | General Electric Company | Turbine blade assembly for retaining sealing and dampening elements |
| US9022727B2 (en) * | 2010-11-15 | 2015-05-05 | Mtu Aero Engines Gmbh | Rotor for a turbo machine |
| US8876478B2 (en) | 2010-11-17 | 2014-11-04 | General Electric Company | Turbine blade combined damper and sealing pin and related method |
| FR2970033B1 (en) * | 2011-01-04 | 2015-10-16 | Turbomeca | METHOD FOR DAMPING GAS TURBINE BLADE AND VIBRATION DAMPER IMPLEMENTATION |
| EP2520768A1 (en) * | 2011-05-02 | 2012-11-07 | MTU Aero Engines AG | Sealing device for an integrated bladed rotor base body of a turbomachine |
| US10287897B2 (en) * | 2011-09-08 | 2019-05-14 | General Electric Company | Turbine rotor blade assembly and method of assembling same |
| US9366142B2 (en) * | 2011-10-28 | 2016-06-14 | General Electric Company | Thermal plug for turbine bucket shank cavity and related method |
| US10113434B2 (en) | 2012-01-31 | 2018-10-30 | United Technologies Corporation | Turbine blade damper seal |
| US9181806B2 (en) | 2012-04-24 | 2015-11-10 | United Technologies Corporation | Airfoil with powder damper |
| US9296039B2 (en) | 2012-04-24 | 2016-03-29 | United Technologies Corporation | Gas turbine engine airfoil impingement cooling |
| US9470095B2 (en) | 2012-04-24 | 2016-10-18 | United Technologies Corporation | Airfoil having internal lattice network |
| US9243502B2 (en) | 2012-04-24 | 2016-01-26 | United Technologies Corporation | Airfoil cooling enhancement and method of making the same |
| US9175570B2 (en) | 2012-04-24 | 2015-11-03 | United Technologies Corporation | Airfoil including member connected by articulated joint |
| US9404369B2 (en) | 2012-04-24 | 2016-08-02 | United Technologies Corporation | Airfoil having minimum distance ribs |
| US9133712B2 (en) | 2012-04-24 | 2015-09-15 | United Technologies Corporation | Blade having porous, abradable element |
| US9074482B2 (en) | 2012-04-24 | 2015-07-07 | United Technologies Corporation | Airfoil support method and apparatus |
| US9249668B2 (en) | 2012-04-24 | 2016-02-02 | United Technologies Corporation | Airfoil with break-way, free-floating damper member |
| US8915718B2 (en) | 2012-04-24 | 2014-12-23 | United Technologies Corporation | Airfoil including damper member |
| US9121286B2 (en) | 2012-04-24 | 2015-09-01 | United Technologies Corporation | Airfoil having tapered buttress |
| US9267380B2 (en) | 2012-04-24 | 2016-02-23 | United Technologies Corporation | Airfoil including loose damper |
| EP2679770A1 (en) * | 2012-06-26 | 2014-01-01 | Siemens Aktiengesellschaft | Platform seal strip for a gas turbine |
| US9587495B2 (en) | 2012-06-29 | 2017-03-07 | United Technologies Corporation | Mistake proof damper pocket seals |
| JP6431839B2 (en) | 2012-06-30 | 2018-11-28 | ゼネラル・エレクトリック・カンパニイ | Turbine blade sealing structure |
| SG11201502166VA (en) * | 2012-09-28 | 2015-05-28 | United Technologies Corp | Seal damper with improved retention |
| US9151165B2 (en) | 2012-10-22 | 2015-10-06 | United Technologies Corporation | Reversible blade damper |
| US9347325B2 (en) * | 2012-10-31 | 2016-05-24 | Solar Turbines Incorporated | Damper for a turbine rotor assembly |
| US20140271205A1 (en) * | 2013-03-12 | 2014-09-18 | Solar Turbines Incorporated | Turbine blade pin seal |
| US10641109B2 (en) | 2013-03-13 | 2020-05-05 | United Technologies Corporation | Mass offset for damping performance |
| EP2971555B1 (en) * | 2013-03-13 | 2021-04-28 | Raytheon Technologies Corporation | Rotor assembly with damper seal between blades |
| US10036260B2 (en) * | 2013-03-13 | 2018-07-31 | United Technologies Corporation | Damper mass distribution to prevent damper rotation |
| US9903434B2 (en) | 2013-08-21 | 2018-02-27 | General Electric Company | Components having vibration dampers enclosed therein and methods of forming such components |
| EP3044420A2 (en) | 2013-09-11 | 2016-07-20 | General Electric Company | Ply architecture for integral platform and damper retaining features in cmc turbine blades |
| WO2015069362A2 (en) | 2013-09-17 | 2015-05-14 | United Technologies Corporation | Gas turbine engine with seal having protrusions |
| US9732620B2 (en) | 2013-09-26 | 2017-08-15 | United Technologies Corporation | Snap in platform damper and seal assembly for a gas turbine engine |
| EP2881544A1 (en) * | 2013-12-09 | 2015-06-10 | Siemens Aktiengesellschaft | Airfoil device for a gas turbine and corresponding arrangement |
| JP6272044B2 (en) * | 2014-01-17 | 2018-01-31 | 三菱重工業株式会社 | Rotor body seal structure, rotor body and rotating machine |
| US9856737B2 (en) * | 2014-03-27 | 2018-01-02 | United Technologies Corporation | Blades and blade dampers for gas turbine engines |
| CN103982250B (en) * | 2014-05-12 | 2015-07-22 | 天津大学 | Metal rubber shock absorber with cooling function |
| US10030530B2 (en) * | 2014-07-31 | 2018-07-24 | United Technologies Corporation | Reversible blade rotor seal |
| US9995162B2 (en) * | 2014-10-20 | 2018-06-12 | United Technologies Corporation | Seal and clip-on damper system and device |
| US9863257B2 (en) * | 2015-02-04 | 2018-01-09 | United Technologies Corporation | Additive manufactured inseparable platform damper and seal assembly for a gas turbine engine |
| US9822644B2 (en) | 2015-02-27 | 2017-11-21 | Pratt & Whitney Canada Corp. | Rotor blade vibration damper |
| US9810075B2 (en) * | 2015-03-20 | 2017-11-07 | United Technologies Corporation | Faceted turbine blade damper-seal |
| US9790809B2 (en) * | 2015-03-24 | 2017-10-17 | United Technologies Corporation | Damper for stator assembly |
| US9920637B2 (en) | 2015-04-07 | 2018-03-20 | United Technologies Corporation | Gas turbine engine damping device |
| JP6554882B2 (en) * | 2015-04-07 | 2019-08-07 | 株式会社Ihi | Shield member and jet engine using the same |
| US10472975B2 (en) * | 2015-09-03 | 2019-11-12 | General Electric Company | Damper pin having elongated bodies for damping adjacent turbine blades |
| US10100648B2 (en) | 2015-12-07 | 2018-10-16 | United Technologies Corporation | Damper seal installation features |
| US10316673B2 (en) | 2016-03-24 | 2019-06-11 | General Electric Company | CMC turbine blade platform damper |
| JP6689117B2 (en) * | 2016-03-31 | 2020-04-28 | 三菱日立パワーシステムズ株式会社 | Stator blade ring and axial flow rotary machine equipped in the axial flow rotary machine |
| EP3438410B1 (en) | 2017-08-01 | 2021-09-29 | General Electric Company | Sealing system for a rotary machine |
| US10746047B2 (en) * | 2017-10-27 | 2020-08-18 | General Electric Company | Structure for mitigating vibratory modes of counter-rotating engine rotors |
| US10927692B2 (en) | 2018-08-06 | 2021-02-23 | General Electric Company | Turbomachinery sealing apparatus and method |
| US10774653B2 (en) | 2018-12-11 | 2020-09-15 | Raytheon Technologies Corporation | Composite gas turbine engine component with lattice structure |
| EP3880936B1 (en) * | 2018-12-20 | 2023-10-18 | Siemens Energy Global GmbH & Co. KG | Bladed rotor system and method of servicing a bladed rotor system |
Family Cites Families (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4101245A (en) * | 1976-12-27 | 1978-07-18 | United Technologies Corporation | Interblade damper and seal for turbomachinery rotor |
| GB1549152A (en) * | 1977-01-11 | 1979-08-01 | Rolls Royce | Rotor stage for a gas trubine engine |
| FR2527260A1 (en) * | 1982-05-18 | 1983-11-25 | Snecma | RETRACTABLE DAMPING DEVICE FOR AUBES OF A TURBOMACHINE |
| JP3230091B2 (en) * | 1990-06-25 | 2001-11-19 | ウェルファイド株式会社 | Method for suppressing coloration of human serum albumin |
| US5228835A (en) * | 1992-11-24 | 1993-07-20 | United Technologies Corporation | Gas turbine blade seal |
| US5415526A (en) * | 1993-11-19 | 1995-05-16 | Mercadante; Anthony J. | Coolable rotor assembly |
| US5460489A (en) | 1994-04-12 | 1995-10-24 | United Technologies Corporation | Turbine blade damper and seal |
| US5573375A (en) * | 1994-12-14 | 1996-11-12 | United Technologies Corporation | Turbine engine rotor blade platform sealing and vibration damping device |
| US5513955A (en) * | 1994-12-14 | 1996-05-07 | United Technologies Corporation | Turbine engine rotor blade platform seal |
| US5827047A (en) * | 1996-06-27 | 1998-10-27 | United Technologies Corporation | Turbine blade damper and seal |
| US5924699A (en) * | 1996-12-24 | 1999-07-20 | United Technologies Corporation | Turbine blade platform seal |
| US5785499A (en) | 1996-12-24 | 1998-07-28 | United Technologies Corporation | Turbine blade damper and seal |
| JPH1181906A (en) | 1997-09-04 | 1999-03-26 | Ishikawajima Harima Heavy Ind Co Ltd | Hybrid buffer body of turbine rotor blade |
| US6273683B1 (en) | 1999-02-05 | 2001-08-14 | Siemens Westinghouse Power Corporation | Turbine blade platform seal |
| US6171058B1 (en) | 1999-04-01 | 2001-01-09 | General Electric Company | Self retaining blade damper |
| JP2001021245A (en) | 1999-07-09 | 2001-01-26 | Irie Koken Kk | Material and device for cold storage |
| US6315298B1 (en) | 1999-11-22 | 2001-11-13 | United Technologies Corporation | Turbine disk and blade assembly seal |
| US6471484B1 (en) | 2001-04-27 | 2002-10-29 | General Electric Company | Methods and apparatus for damping rotor assembly vibrations |
-
2004
- 2004-09-13 US US10/939,766 patent/US7121800B2/en active Active
-
2005
- 2005-05-10 SG SG200502935A patent/SG121034A1/en unknown
- 2005-05-11 CA CA002507086A patent/CA2507086A1/en not_active Abandoned
- 2005-05-20 KR KR1020050042237A patent/KR20060048029A/en not_active Application Discontinuation
- 2005-05-24 AU AU2005202260A patent/AU2005202260B2/en not_active Expired - Fee Related
- 2005-06-10 NO NO20052830A patent/NO20052830L/en not_active Application Discontinuation
- 2005-07-12 JP JP2005202609A patent/JP2006077759A/en active Pending
- 2005-07-13 CN CNA2005100832831A patent/CN1749531A/en active Pending
- 2005-07-13 EP EP05254378A patent/EP1635037A3/en not_active Withdrawn
Also Published As
| Publication number | Publication date |
|---|---|
| EP1635037A2 (en) | 2006-03-15 |
| SG121034A1 (en) | 2006-04-26 |
| US20060056974A1 (en) | 2006-03-16 |
| CN1749531A (en) | 2006-03-22 |
| US7121800B2 (en) | 2006-10-17 |
| JP2006077759A (en) | 2006-03-23 |
| AU2005202260B2 (en) | 2007-05-10 |
| AU2005202260A1 (en) | 2006-03-30 |
| EP1635037A3 (en) | 2009-06-24 |
| NO20052830L (en) | 2006-03-14 |
| NO20052830D0 (en) | 2005-06-10 |
| KR20060048029A (en) | 2006-05-18 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US7121800B2 (en) | Turbine blade nested seal damper assembly | |
| US20090004013A1 (en) | Turbine blade nested seal and damper assembly | |
| EP0851097B1 (en) | Turbine blade damper and seal | |
| EP2163725B1 (en) | Turbine blade damper arrangement | |
| JP4460103B2 (en) | Self-retaining blade damper | |
| US7520718B2 (en) | Seal and locking plate for turbine rotor assembly between turbine blade and turbine vane | |
| EP1867837B1 (en) | Bucket vibration damper system | |
| US5281097A (en) | Thermal control damper for turbine rotors | |
| US7270517B2 (en) | Turbine blade with vibration damper | |
| JP5702783B2 (en) | Vibration damping shim for fan blades | |
| JP4017216B2 (en) | Turbine blade damper and seal | |
| EP1451446B1 (en) | Turbine blade pocket shroud | |
| US6409472B1 (en) | Stator assembly for a rotary machine and clip member for a stator assembly | |
| EP2472065B1 (en) | Damper coverplate and sealing arrangement for turbine bucket shank | |
| RU2487249C2 (en) | Gas turbine rotor disc, gas turbine engine with said disc, and blade root strap | |
| US7942636B2 (en) | Annulus filler seal | |
| US5460489A (en) | Turbine blade damper and seal | |
| JPH08232602A (en) | Rotor assembly for axial-flow turbine engine | |
| JPH02211302A (en) | Component retaining structure of turbine rotter | |
| KR101828637B1 (en) | Method for mounting shielding on a turbine casing, and mounting assembly for implementing same | |
| JPH0477121B2 (en) | ||
| JPH04129804U (en) | Turbine blade sealing device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| EEER | Examination request | ||
| FZDE | Discontinued |